scholarly journals Thrust characteristics of compact high-voltage pulsed plasma thruster utilizing liquid propellant

2021 ◽  
Vol 2064 (1) ◽  
pp. 012114
Author(s):  
S A Buldashev ◽  
R V Emlin ◽  
P A Morozov ◽  
I F Punanov ◽  
Ye N Shcherbakov ◽  
...  
Keyword(s):  
High Voltage ◽  
Ferroelectric Ceramics ◽  
Magnetic Storage ◽  
Pulsed Plasma ◽  
Liquid Propellant ◽  
Voltage Transformer ◽  
Pulsed Plasma Thruster ◽  
Plasma Thruster ◽  
Thrust Characteristics ◽  
Discharge Unit

Abstract In this work, we present the results on thrust performance of 0.5 kg sub-joule pulsed plasma thruster prototype based on a high-voltage transformer with magnetic storage capable of work at frequency of 400 Hz. The discharge unit is made of ferroelectric ceramics with an option for utilizing liquid propellant. In case of vacuum oil as a propellant, we obtained values of thrust of ~ 80 nN·s per discharge and 33 μN·s for 400 pulses in 1 second.

Effect of solute mixing in the liquid propellant of a pulsed plasma thruster

Vacuum ◽  
2006 ◽  
Vol 80 (11-12) ◽  
pp. 1234-1238 ◽  
Author(s):  
Hiroyuki Koizumi ◽  
Yoko Kawazoe ◽  
Kimiya Komurasaki ◽  
Yoshihiro Arakawa
Keyword(s):  
Pulsed Plasma ◽  
Liquid Propellant ◽  
Pulsed Plasma Thruster ◽  
Plasma Thruster ◽  
Solute Mixing

Performance Study on Liquid Propellant Pulsed Plasma Thruster

2003 ◽  
Author(s):  
Akira Kakami ◽  
Hiroyuki Koizumi ◽  
Yohei Furuta ◽  
Kimiya Komurasaki ◽  
Yoshihiro Arakawa
Keyword(s):  
Pulsed Plasma ◽  
Performance Study ◽  
Liquid Propellant ◽  
Pulsed Plasma Thruster ◽  
Plasma Thruster

Design and performance of liquid propellant pulsed plasma thruster

Vacuum ◽  
2004 ◽  
Vol 73 (3-4) ◽  
pp. 419-425 ◽  
Author(s):  
Akira Kakami ◽  
Hiroyuki Koizumi ◽  
Kimiya Komurasaki ◽  
Yoshihiro Arakawa
Keyword(s):  
Pulsed Plasma ◽  
Liquid Propellant ◽  
Pulsed Plasma Thruster ◽  
Plasma Thruster ◽  
And Performance

scholarly journals Liquid micro pulsed plasma thruster

Nukleonika ◽  
2015 ◽  
Vol 60 (2) ◽  
pp. 257-261 ◽  
Author(s):  
Agnieszka Szelecka ◽  
Jacek Kurzyna ◽  
Dariusz Daniłko ◽  
Serge Barral
Keyword(s):  
Solid Propellant ◽  
Power Ratio ◽  
Pulsed Plasma ◽  
Small Satellite ◽  
Liquid Propellant ◽  
Pulsed Plasma Thruster ◽  
Plasma Thruster ◽  
Volatile Liquid ◽  
New Type

Abstract A new type of pulsed plasma thruster (PPT) for small satellite propulsion is investigated, of which the most innovative aspect is the use of a non-volatile liquid propellant. The thruster is based on an open capillary design. The thruster achieved a thrust-to-power ratio above 45 μN/W, which constitutes a 5-fold improvement over the water-propelled pulsed plasma thruster, and which is also slightly above the performance of a similarly sized PPT with a solid propellant.

Sign in / Sign up

Export Citation Format

Share Document